Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations 65879 

applicant than the terms and conditions 

that are generally applicable to 

residential real property loans offered 

by the same lender to other borrowers 

in comparable circumstances. 

(iii) A covered employee who seeks or 

obtains a real property loan from a 

national bank, Federal savings 

association or a subsidiary of a national 

bank or Federal savings association or 

whose spouse or minor child obtains a 

real property loan under the 

requirements of paragraph (b)(4)(ii) 

above must observe from the time of the 

initial application any recusal 

established under OCC ethics policy. 

(5) Pre-existing credit. (i) This section 

does not prohibit a covered OCC 

employee, or spouse or minor child of 

a covered OCC employee from retaining 

a loan or extension of credit from a 

national bank or Federal savings 

association on its original terms, and 

subject to any recusal established under 

OCC ethics policy, if the loan or 

extension of credit: 

(A) Was incurred prior to employment 

by the OCC; 

(B) Was obtained from a lender that 

was not supervised by the OCC at the 

time it was obtained; or 

(C) Is held by a national bank or 

Federal savings association or 

subsidiary thereof as the result of the 

sale or transfer of a loan to the national 

bank or Federal savings association or 

the conversion or merger of the lender 

into a national bank or Federal savings 

association. 

(ii) Any renewal or renegotiation of a 

pre-existing loan or extension of credit 

will be treated as a new loan subject to 

the prohibitions in paragraph (b)(1) of 

this section. 

* * * * * 

(d) Prohibited recommendations. 

Employees of the OCC shall not make 

recommendations or suggestions, 

directly or indirectly, concerning the 

acquisition or sale or other divestiture of 

securities of any commercial bank 

(including both national and statechartered banks), Federal savings 

association, state savings association, 

affiliate of these institutions (including 

bank holding companies, savings and 

loan holding companies, and any nonbank subsidiaries of either type of 

holding company), or foreign bank that 

owns a commercial bank or savings 

association in the United States. 

(e) Prohibited purchase of assets. No 

employee of the OCC, or spouse or 

minor child of an OCC employee, shall 

purchase, directly or indirectly, an asset 

(i.e. real property, automobiles, 

furniture, or similar items) from a 

national bank or Federal savings 

association or an affiliate of a national 

bank or a Federal savings association, 

including a bank or savings and loan 

holding company, unless it is sold at a 

public auction or by other means which 

ensure that the selling price is the 

asset’s fair market value. 

(f) Outside employment—(1) 

Prohibition on Outside Employment. No 

covered OCC employee shall perform 

services for compensation for any bank, 

savings association or a bank or savings 

association affiliate, or for any officer, 

director or employee of, or for any 

person connected in any capacity with 

a bank, savings association or bank or 

savings association affiliate. 

(2) * * * 

(i) An OCC examiner; and 

* * * * * 

§ 3101.109 [Removed] 

■ 5. Remove § 3101.109. 

§ 3101.110 [Removed] 

■ 6. Remove § 3101.110. 

§ 3101.111 [Removed] 

■ 7. Remove reserved § 3101.111. 

Dated: October 14, 2014. 

By the Department of the Treasury. 

Christopher J. Meade, 

General Counsel. 

Dated: October 24, 2014. 

By the Office of Government Ethics. 

Walter M. Shaub, 

Director. 

[FR Doc. 2014–26173 Filed 11–5–14; 8:45 am] 

BILLING CODE 4810–25–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2013–0894; Special 

Conditions No. 25–532–SC] 

Special Conditions: Airbus A350–900 

Series Airplane; Interaction of Systems 

and Structures 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions, request 

for comments; correction. 

SUMMARY: This document corrects errors 

that appeared in final special conditions 

docket no. FAA–2013–0894, which was 

published in the Federal Register on 

December 20, 2013 (78 FR 76980). The 

errors are in the document’s special 

conditions stage (notice vs. final) and 

special conditions number. 

DATES: This action is effective 

November 6, 2014. 

FOR FURTHER INFORMATION CONTACT: 

Todd Martin, FAA, Airframe/Cabin 

Safety, ANM–115, Transport Airplane 

Directorate, Aircraft Certification 

Service, 1601 Lind Avenue SW., 

Renton, Washington, 98057–3356; 

telephone (425) 227–1178; facsimile 

(425) 227–1320. 

SUPPLEMENTARY INFORMATION: The final 

special conditions document designated 

as ‘‘Docket No. FAA–2013–0894; Notice 

No. 25–13–16–SC’’ was published in the 

Federal Register on December 20, 2013 

(78 FR 76980). The document issued 

special conditions pertaining to 

interaction of systems and structures on 

Airbus A350–900 series airplanes. 

As published, the document 

contained two errors: One referring to 

the document’s special conditions stage, 

‘‘Notice no.,’’ instead of ‘‘Special 

Conditions No.;’’ and one in the special 

conditions number itself, 25–13–16–SC 

(a notice number), instead of 25–532–SC 

(the assigned final special conditions 

number). 

Because this error and correction do 

not affect the regulatory content of the 

special conditions, the special 

conditions are not being re-published. 

Correction 

In the final special conditions, request 

for comments document [FR Doc. 2013– 

30235, Filed 12–19–13; 8:45 a.m.] 

published on December 20, 2013 (78 FR 

76980), make the following correction: 

On page 76980, in the first column, in 

the heading, correct ‘‘Notice No. 25–13– 

16–SC’’ to read ‘‘Special Conditions No. 

25–532–SC’’. 

Issued in Renton, Washington, on October 

31, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–26341 Filed 11–5–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1064; Directorate 

Identifier 2012–NM–101–AD; Amendment 

39–17991; AD 2014–20–18] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 


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SUMMARY: We are superseding 

Airworthiness Directive (AD) 2005–23– 

08 for certain Airbus Model A300 B4– 

605R and B4–622R airplanes; Model 

A300 F4–605R airplanes; and Model 

A300 C4–605R Variant F airplanes. AD 

2005–23–08 required repetitive 

inspections to detect cracks of certain 

attachment holes, installation of new 

fasteners, follow-on inspections or 

repair if necessary, and modification of 

the angle fittings of fuselage frame FR47. 

This new AD adds new repetitive 

ultrasonic inspections for cracks of the 

center wing box lower panel; and repair 

if necessary. This new AD also removes 

certain airplanes from the applicability. 

This AD was prompted by reports of 

cracks found on the horizontal flange of 

the Frame 47 internal corner angle 

fitting while accomplishing the 

modification required by AD 2005–23– 

08. We are issuing this AD to detect and 

correct fatigue cracking of the forward 

fitting of fuselage frame FR47, which 

could result in reduced structural 

integrity of the frame. 

DATES: This AD becomes December 11, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 11, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of December 19, 2005 (70 FR 

69056, November 14, 2005). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of July 8, 2002 (67 FR 38193, 

June 3, 2002). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-1064; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax 

+33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: (425) 227–2125; 

fax: (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2005–23–08, 

Amendment 39–14366 (70 FR 69056, 

November 14, 2005). AD 2005–23–08 

applied to certain Model A300 B4–601, 

B4–603, B4–620, and B4–622 airplanes; 

Model A300 B4–605R and B4–622R 

airplanes; Model A300 F4–605R 

airplanes; and Model A300 C4–605R 

Variant F airplanes. The NPRM 

published in the Federal Register on 

December 26, 2013 (78 FR 78285). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0092, 

dated May 25, 2012; Correction dated 

June 4, 2012 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’); to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Prompted by cracks found on the Frame 47 

angle fitting, DGAC France published AD 

2000–533–328 [http://ad.easa.europa.eu/ad/

F-2000-533-328R1] to require [a] repetitive 

inspection programme for fuselage frame 47. 

If not detected and corrected, these cracks 

could affect the structural integrity of the 

Centre Wing Box (CWB) of the aeroplane. 

Subsequent to the publication of a new 

repetitive inspection programme for fuselage 

frame 47 at certain fasteners of the CWB 

angle fitting, DGAC France issued AD F– 

2004–159 [http://ad.easa.europa.eu/ad/F2004-159] [which corresponds to AD 2005– 

23–08, Amendment 39–14366 (70 FR 69056, 

November 14, 2005)], superseding AD 2000– 

533–328. 

After DGAC France AD F–2004–159 was 

issued, cracks were reportedly found on the 

horizontal flange of the Frame 47 internal 

corner angle fitting during accomplishment 

of routine maintenance structural inspection 

and modification in accordance with Airbus 

SB A300–57–6050. 

Prompted by these findings, Airbus 

reviewed and amended the inspection 

programme for the internal lower angle 

fitting flange (horizontal face). The 

inspection programme for the lower angle 

fitting web (vertical face) related to SB A300– 

57–6049 and internal lower angle fitting 

modification programme related to SB A300– 

57–6050 remain unchanged. 

For the reasons explained above, this new 

[EASA] AD retains the requirements of DGAC 

France AD F–2004–159, which is 

superseded, and requires additional 

repetitive [ultrasonic] inspections [for cracks] 

of the CWB lower panel through the 

ultrasonic method and, depending on 

findings, [e.g., repair] re-installation of 

removed fasteners in transition fit instead of 

interference. 

This [EASA] AD has been republished to 

correct a typographical error * * *. 

The repetitive interval for the new 

ultrasonic inspection is either 1,260 

flight cycles or 2,720 flight hours, 

whichever occurs first; or 1,360 flight 

cycles or 2,200 flight hours, whichever 

occurs first; depending on average flight 

time of the airplane. You may examine 

the MCAI in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-1064- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (78 FR 78285, 

December 26, 2013) and the FAA’s 

response to each comment. 

Requests To Remove Requirement To 

Refer to This AD in Repair Approvals 

Airlines for America, Inc. (A4A), on 

behalf of seven affected member 

airlines, requested that we revise 

paragraphs (m)(1), (m)(2), and (o)(2) of 

the NPRM (78 FR 78285, December 26, 

2013) to remove the requirement to 

include the AD reference in repair 

approvals. The commenters have made 

this request because the proposed 

requirement is overly broad and would 

add significant cost and complexity to 

their operations. The commenters were 

concerned that this proposed 

requirement would set a precedent for 

how repairs are approved, and could 

negatively affect all U.S. operators of 

foreign-manufactured airplanes. 

We concur with the commenters’ 

request to remove from this AD the 

requirement that repair approvals must 

specifically refer to this AD. 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. The MCAI or referenced 

service information in an FAA AD often 

directs the owner/operator to contact 

the manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (78 FR 78285, December 

26, 2013), we proposed to prevent the 


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use of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include ‘‘the Design Approval Holder 

(DAH) with a State of Design 

Authority’s design organization 

approval (DOA)’’ to refer to a DAH 

authorized to approve required repairs 

for the proposed AD. 

One commenter to the NPRM (78 FR 

78285, December 26, 2013), United 

Parcel Service (UPS), stated the 

following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed 

that paragraph and retitled it 

‘‘Contacting the Manufacturer.’’ This 

paragraph now clarifies that for any 

requirement in this AD to obtain 

corrective actions from a manufacturer, 

the actions must be accomplished using 

a method approved by the FAA, EASA, 

or Airbus’s EASA DOA. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility afforded previously by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the AD 

Implementation Aviation Rulemaking 

Committee to increase flexibility in 

complying with ADs by identifying 

those actions in manufacturers’ service 

instructions that are ‘‘Required for 

Compliance’’ with ADs. We continue to 

work with manufacturers to implement 

this recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Other commenters pointed out that in 

many cases the foreign manufacturer’s 

service bulletin and the foreign 

authority’s MCAI may have been issued 

some time before the FAA AD. 

Therefore, the DOA may have provided 

U.S. operators with an approved repair, 

developed with full awareness of the 

unsafe condition, before the FAA AD is 

issued. Under these circumstances, to 

comply with the FAA AD, the operator 

would be required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time, and 

expense to the compliance process with 

no safety benefit. 

Based on these comments, we 

removed from this AD the requirement 

that the DAH-provided repair 

specifically refer to this AD. Before 

adopting such a requirement in the 

future, the FAA will coordinate with 

affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 

unsafe condition addressed in the AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. 

We have also decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or the ‘‘DAH with 

State of Design Authority design 

organization approval’’ for new 

requirements, but instead we will 

provide the specific delegation approval 

granted by the State of Design Authority 

for the DAH. 

Request To Revise Costs of Compliance 

One commenter, FedEx, requested 

assurance that two inspections (the 

rotating probe of the attachment holes of 

the horizontal flange of the internal 

corner angle fitting, and the ultrasonic 

inspection of the aft bottom panel of the 

center wing box) specified in the NPRM 

(78 FR 78285, December 26, 2013) are to 

be conducted as two separate 

inspections at two separate thresholds 

and intervals. FedEx observed that both 

inspections are contained in the same 

service information, and that these two 

inspections appear to be combined in 

the Costs of Compliance paragraph of 

the NPRM. FedEx requested that the 

estimated costs be presented separately 

for the two inspection actions, and 

added that the Costs of Compliance 

paragraph should specify 4 work-hours 

for the new ultrasonic inspection. 

We agree to clarify the Costs of 

Compliance paragraph. There are two 

inspection actions (rotating probe and 

ultrasonic inspections) identified in 

Airbus Service Bulletin A300–57–6086, 

Revision 05, dated January 30, 2012, 

and these are listed separately in the 

Costs of Compliance paragraph. The 

second row of the table in the Costs of 

Compliance paragraph should reflect 

the costs for the rotating probe 

inspections identified in Airbus Service 

Bulletin A300–57–6086, Revision 05, 

dated January 30, 2012; we have revised 

the second row of the table in the Costs 

of Compliance paragraph accordingly. 

We have also revised the fourth row of 

the table in the Costs of Compliance 

paragraph to refer to Airbus Service 

Bulletin A300–57–6086, Revision 05, 

dated January 30, 2012, to reflect costs 

for the new ultrasonic inspection. 

In addition, we agree with FedEx that 

the ultrasonic inspection takes 4 workhours, as specified in Airbus Service 

Bulletin A300–57–6086, Revision 05, 

dated January 30, 2012. In addition, 

Airbus Service Bulletin A300–57–6086, 

Revision 05, dated January 30, 2012, 

specifies 12 work-hours for access and 

close procedures. Therefore, we have 

revised the work-hours for the 

ultrasonic inspection specified in the 

fourth row of the table in the Costs of 

Compliance paragraph from 35 to 16 

work-hours. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these changes: 


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• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

78285, December 26, 2013) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 78285, 

December 26, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 65 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per airplane 

Inspection for attachment holes on internal angles [retained action from AD 2005–23–08, 

Amendment 39–14366 (70 FR 69056, November 14, 2005)].

13 ................................. $85 $0 ................................. $1,105. 

Rotating probe inspections for attachment holes 

in the horizontal flange (specified in Airbus 

Service Bulletin A300–57–6086, Revision 05, 

dated January 30, 2012) [retained action 

from AD 2005–23–08, Amendment 39–14366 

(70 FR 69056, November 14, 2005)].

30 ................................. 85 Between $6,637 and 

$19,091.

Between $9,187 and 

$21,641 per inspection 

cycle. 

Modification [retained action from AD 2005–23– 

08, Amendment 39–14366 (70 FR 69056, 

November 14, 2005)].

Between 65 and 365 ... 85 $3,370 .......................... Between $8,895 and 

$34,395. 

New ultrasonic inspections of the aft bottom 

panel of the center wing box (specified in Airbus Service Bulletin A300–57–6086, Revision 

05, dated January 30, 2012).

16 ................................. 85 Between $11,750 and 

$18,720.

Between $13,110 and 

$20,080 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-1064; or in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 


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Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations 65883 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2005–23–08, Amendment 39–14366 (70 

FR 69056, November 14, 2005), and 

adding the following new AD: 

2014–20–18 Airbus: Amendment 39–17991. 

Docket No. FAA–2013–1064; Directorate 

Identifier 2012–NM–101–AD. 

(a) Effective Date 

This AD becomes effective December 11, 

2014. 

(b) Affected ADs 

This AD replaces AD 2005–23–08, 

Amendment 39–14366 (70 FR 69056, 

November 14, 2005). 

(c) Applicability 

This AD applies to Airbus Model B4–603, 

B4–620, and B4–622 airplanes; Model A300 

B4–605R and B4–622R airplanes; Model 

A300 F4–605R airplanes; and Model A300 

C4–605R Variant F airplanes; certificated in 

any category; except airplanes on which 

Airbus Modification 12171 or 12249 has been 

embodied in production, or on which Airbus 

Service Bulletin A300–57–6069 has been 

embodied in service. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports of cracks 

found on the horizontal flange of the Frame 

47 internal corner angle fitting while 

accomplishing the modification required by 

AD 2005–23–08, Amendment 39–14366 (70 

FR 69056, November 14, 2005). We are 

issuing this AD to detect and correct fatigue 

cracking of the forward fitting of fuselage 

frame FR47, which could result in reduced 

structural integrity of the frame. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Inspections for Attachment 

Holes on the Internal Angles of the Wing 

Center Box, and Corrective Action 

This paragraph restates the requirements of 

paragraphs (f), (g), and (h) of AD 2005–23– 

08, Amendment 39–14366 (70 FR 69056, 

November 14, 2005), with revised service 

information. Perform a rotating probe 

inspection to detect cracking of the 

applicable attachment holes on the left and 

right internal angles of the wing center box 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6049, Revision 06, dated July 15, 2004; or 

Airbus Service Bulletin A300–57–6049, 

Revision 07, dated December 22, 2006. Do 

the inspection at the applicable time 

specified by paragraph 1.E.(2), 

Accomplishment Timescale, of Airbus 

Service Bulletin A300–57–6049, Revision 06, 

dated July 15, 2004; except as required by 

paragraph (j) of this AD. Repeat the rotating 

probe inspection specified in this paragraph 

thereafter at intervals not to exceed the 

applicable interval specified in Airbus 

Service Bulletin A300–57–6049, Revision 06, 

dated July 15, 2004, except that all touchand-go landings must be counted in 

determining the total number of flight cycles 

between consecutive inspections. As of the 

effective date of this AD, only Airbus Service 

Bulletin A300–57–6049, Revision 07, dated 

December 22, 2006, may be used to 

accomplish the actions required by this 

paragraph. 

(1) If no cracking is found during any 

inspection required by paragraph (g) of this 

AD: Prior to further flight, install new 

fasteners in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6049, Revision 06, 

dated July 15, 2004; or Airbus Service 

Bulletin A300–57–6049, Revision 07, dated 

December 22, 2006. As of the effective date 

of this AD, only Airbus Service Bulletin 

A300–57–6049, Revision 07, dated December 

22, 2006, may be used to accomplish the 

actions required by this paragraph. 

(2) If any cracking is found during any 

inspection required by paragraph (g) of this 

AD: Prior to further flight, perform applicable 

corrective actions (including reaming, 

drilling, drill-stopping holes, chamfering, 

performing follow-on inspections, and 

installing new or oversize fasteners), in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6049, Revision 06, dated July 15, 2004; or 

Airbus Service Bulletin A300–57–6049, 

Revision 07, dated December 22, 2006; 

except as required by paragraph (k) of this 

AD. As of the effective date of this AD, only 

Airbus Service Bulletin A300–57–6049, 

Revision 07, dated December 22, 2006, may 

be used to accomplish the actions required 

by this paragraph. 

(h) Retained Inspections for Attachment 

Holes in the Horizontal Flange of the 

Internal Corner Angle Fitting of Fuselage 

Frame FR47, and Corrective Action 

This paragraph restates the requirements of 

paragraphs (i), (j), and (k) of AD 2005–23–08, 

Amendment 39–14366 (70 FR 69056, 

November 14, 2005), with revised service 

information. Perform a rotating probe 

inspection to detect cracking of the 

applicable attachment holes in the horizontal 

flange of the internal corner angle fitting of 

fuselage frame FR47, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6086, Revision 01, 

dated April 2, 2002; or Airbus Service 

Bulletin A300–57–6086, Revision 05, dated 

January 30, 2012. Do the inspection at the 

applicable time specified in paragraph 1.E., 

Compliance, of Airbus Service Bulletin 

A300–57–6086, Revision 01, dated April 2, 

2002, except as provided by paragraph (j) of 

this AD; or within 1,500 flight cycles after 

July 8, 2002 (the effective date of AD 2002– 

11–04, Amendment 39–12765 (67 FR 38193, 

June 3, 2002)); whichever occurs later. Repeat 

the rotating probe inspection specified in this 

paragraph thereafter at intervals not to 

exceed the applicable interval specified in 

Airbus Service Bulletin A300–57–6086, 

dated June 6, 2000, except that all touch-andgo landings must be counted in determining 

the total number of flight cycles between 

consecutive inspections. As of the effective 

date of this AD, only Airbus Service Bulletin 

A300–57–6086, Revision 05, dated January 

30, 2012, may be used to accomplish the 

actions required by this paragraph. 

(1) If no cracking is found during any 

inspection required by paragraph (h) of this 

AD: Prior to further flight, install new 

fasteners in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6086, Revision 01, 

dated April 2, 2002; or Airbus Service 

Bulletin A300–57–6086, Revision 05, dated 

January 30, 2012. As of the effective date of 

this AD, only Airbus Service Bulletin A300– 

57–6086, Revision 05, dated January 30, 

2012, may be used to accomplish the actions 

required by this paragraph. 

(2) If any cracking is found during any 

inspection required by paragraph (h) of this 

AD: Prior to further flight, perform applicable 

corrective actions (including inspecting hole 

T if any cracking is found at hole G, reaming 

the holes, and installing oversize fasteners), 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6086, Revision 01, dated April 2, 2002; or 

Airbus Service Bulletin A300–57–6086, 

Revision 05, dated January 30, 2012; except 

as required by paragraph (k) of this AD. As 

of the effective date of this AD, only Airbus 

Service Bulletin A300–57–6086, Revision 05, 

dated January 30, 2012, may be used to 

accomplish the actions required by this 

paragraph. 

(i) Retained Modification of Angle Fittings of 

the Wing Center Box 

This paragraph restates the requirements of 

paragraph (l) of AD 2005–23–08, Amendment 

39–14366 (70 FR 69056, November 14, 2005). 

Modify the left and right internal angle 

fittings of the wing center box. The 

modification includes performing a rotating 

probe inspection to detect cracking, repairing 

cracks, cold expanding holes, and installing 

medium interference fitting bolts. Perform 

the modification in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6050, Revision 03, 

dated May 31, 2001; and at the applicable 

time specified by paragraph 1.B.(4), 

Accomplishment Timescale, of Airbus 

Service Bulletin A300–57–6050, Revision 03, 

dated May 31, 2001; except as required by 

paragraphs (j) and (k) of this AD. 

(j) Retained Compliance Time Exception to 

Service Information Specified in Paragraphs 

(g), (h), and (i) of This AD 

This paragraph restates the requirements of 

paragraph (m) of AD 2005–23–08, 

Amendment 39–14366 (70 FR 69056, 

November 14, 2005). Where the service 

information specified in paragraphs (g), (h), 

and (i) of this AD specify a grace period 

relative to receipt of the service bulletin, this 

AD requires compliance within the 

applicable grace period following December 

19, 2005 (the effective date of AD 2005–23– 

08), if the threshold has been exceeded. 


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(k) Retained Corrective Action Exception to 

Service Information Specified in Paragraphs 

(g), (h), and (i) of This AD 

This paragraph restates the requirements of 

paragraph (n) of AD 2005–23–08, 

Amendment 39–14366 (70 FR 69056, 

November 14, 2005). If any crack is detected 

during any inspection required by paragraph 

(g), (h), or (i) of this AD, and the applicable 

service information specifies to contact the 

manufacturer for disposition of certain 

corrective actions: Prior to further flight, 

repair in accordance with a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) (or its delegated agent). 

(l) Credit for Previous Actions 

(1) This paragraph restates the credit 

provided by paragraph (o) of AD 2005–23–08, 

Amendment 39–14366 (70 FR 69056, 

November 14, 2005): This paragraph provides 

credit for actions required by paragraph (h) 

of this AD, if those actions were performed 

before December 19, 2005 (the effective date 

of AD 2005–23–08), using Airbus Service 

Bulletin A300–57–6086, dated June 6, 2000. 

(2) This paragraph restates the credit 

provided by paragraph (p) of AD 2005–23– 

08, Amendment 39–14366 (70 FR 69056, 

November 14, 2005): This paragraph provides 

credit for the modification required by 

paragraph (i) of this AD, if the modification 

was performed before December 19, 2005 (the 

effective date of AD 2005–23–08), using 

Airbus Service Bulletin A300–57–6050, 

Revision 02, dated February 10, 2000. 

(m) New Requirements of This AD: 

Repetitive Ultrasonic Inspections and 

Corrective Action 

(1) For airplanes on which Airbus Service 

Bulletin A300–57–6050, Revision 03, dated 

May 31, 2001, has not been done, or on 

which Airbus Modification 10155 has been 

done: Perform an ultrasonic inspection for 

cracking of the left- and right-hand aft bottom 

panel of the center wing box (CWB), in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6086, Revision 05, dated January 30, 

2012. Do the inspection at the later of the 

times specified in paragraphs (m)(1)(i) and 

(m)(1)(ii) of this AD. If any cracking is found, 

before further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). Repeat 

the inspection thereafter at intervals not to 

exceed the applicable interval specified in 

paragraph 1.E.(2), Accomplishment 

Timescale, of Airbus Service Bulletin A300– 

57–6086, Revision 05, dated January 30, 

2012. 

(i) Within 13,400 flight cycles or 34,600 

flight hours after the first flight of the 

airplane, whichever occurs first. 

(ii) Within 650 flight cycles or 8 months 

after the effective date of this AD, whichever 

occurs first. 

(2) For airplanes on which Airbus Service 

Bulletin A300–57–6050, Revision 03, dated 

May 31, 2001, has been done: Perform an 

ultrasonic inspection for cracking of the leftand right-hand aft bottom panel of the center 

wing box (CWB), in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6086, Revision 05, 

dated January 30, 2012. Do the inspection at 

the later of the times specified in paragraphs 

(m)(2)(i) and (m)(2)(ii) of this AD. If any 

cracking is found, before further flight, repair 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

Repeat the inspection thereafter at intervals 

not to exceed the applicable interval 

specified in paragraph 1.E.(2), 

Accomplishment Timescale, of Airbus 

Service Bulletin A300–57–6086, Revision 05, 

dated January 30, 2012. 

(i) Within 13,400 flight cycles or 34,600 

flight hours after accomplishing Airbus 

Service Bulletin A300–57–6050, whichever 

occurs first. 

(ii) Within 650 flight cycles or 8 months 

after the effective date of this AD, whichever 

occurs first. 

(n) New Reporting Requirement 

Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (m) of this AD to the 

Design Approval Holder, at the applicable 

time specified in paragraph (n)(1) or (n)(2) of 

this AD. The report must include the 

inspection results, a description of any 

discrepancies found, the airplane serial 

number, and the number of flight cycles and 

flight hours on the airplane. The inspection 

report form in Appendix 01 of Airbus Service 

Bulletin A300–57–6086, Revision 05, dated 

January 30, 2012, may be used. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–2125; fax: 425–227– 

1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(ii) AMOCs approved previously in 

accordance with AD 2005–23–08, 

Amendment 39–14366 (70 FR 69056, 

November 14, 2005), are approved as AMOCs 

for the corresponding provision of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) 2012– 

0092, dated May 25, 2012; Correction dated 

June 4, 2012; for related information. You 

may examine the MCAI in the AD docket on 

the Internet at http://www.regulations.gov/ 

#!documentDetail;D=FAA-2013-10640002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (q)(5) and (q)(6) of this AD. 

(q) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on December 11, 2014. 

(i) Airbus Service Bulletin A300–57–6049, 

Revision 07, dated December 22, 2006. 

(ii) Airbus Service Bulletin A300–57–6086, 

Revision 05, dated January 30, 2012. 

(4) The following service information was 

approved for IBR on December 19, 2005 (70 

FR 69056, November 14, 2005). 

(i) Airbus Service Bulletin A300–57–6049, 

excluding Appendix 01, Revision 06, dated 

July 15, 2004. 


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Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations 65885 

(ii) Airbus Service Bulletin A300–57–6050, 

Revision 03, dated May 31, 2001. This 

document contains the effective pages 

specified in paragraphs (q)(4)(ii)(A), 

(q)(4)(ii)(B), (q)(4)(ii)(C), and (q)(4)(ii)(D) of 

this AD. 

(A) Pages 1, 4, 10A through 11, 75, and 76 

are identified as Revision 03, dated May 31, 

2001. 

(B) Pages 2, 8, 9, 17 through 32, 41, 42, 57, 

58, 61 through 63, and 77 are identified as 

Revision 02, dated February 10, 2000. 

(C) Pages 3, 5 through 7, 10, 12, 33, 34, 37, 

38, 47, 59, and 60 are identified as Revision 

01, dated May 31, 1999. 

(D) Pages 13 through 16, 35, 36, 39, 40, 43 

through 46, 48 through 56, and 64 through 

74 are identified as original, dated September 

9, 1994. 

(iii) Airbus Service Bulletin A300–57– 

6086, Revision 01, dated April 2, 2002. 

(5) The following service information was 

approved for IBR on July 8, 2002 (67 FR 

38193, June 3, 2002). 

(i) Airbus Service Bulletin A300–57–6086, 

dated June 6, 2000. 

(ii) Reserved. 

(6) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(7) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(8) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 24, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–26356 Filed 11–5–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0288; Directorate 

Identifier 2013–NM–101–AD; Amendment 

39–18009; AD 2014–22–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model DC–9–10, 

DC–9–20, and DC–9–30 series airplanes. 

This AD was prompted by an evaluation 

by the design approval holder (DAH) 

indicating that the improved (shotpeened) aft fuselage non-ventral 

pressure bulkhead tee is subject to 

widespread fatigue damage (WFD). This 

AD requires repetitive inspections for 

cracking of the improved (shot-peened) 

non-ventral aft pressure bulkhead tees, 

and replacement if necessary. We are 

issuing this AD to detect and correct 

fatigue cracking of the improved (shotpeened) non-ventral aft pressure 

bulkhead tees connecting the bulkhead 

web to the fuselage, which could result 

in reduced structural integrity and rapid 

decompression of the airplane. 

DATES: This AD is effective December 

11, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 11, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; Internet https:// 

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0288; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Eric 

Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

CA 90712–4137; phone: 562–627–5348; 

fax: 562–627–5210; email: 

eric.schrieber@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model DC–9–10, DC–9–20, and DC–9– 

30 series airplanes. The NPRM 

published in the Federal Register on 

May 29, 2014 (79 FR 30753). The NPRM 

was prompted by an evaluation by the 

DAH indicating that the improved (shotpeened) aft fuselage non-ventral 

pressure bulkhead tee is subject to WFD. 

The NPRM proposed to require 

repetitive inspections for cracking of the 

improved (shot-peened) non-ventral aft 

pressure bulkhead tees, and 

replacement if necessary. We are issuing 

this AD to detect and correct fatigue 

cracking of the improved (shot-peened) 

non-ventral aft pressure bulkhead tees 

connecting the bulkhead web to the 

fuselage, which could result in reduced 

structural integrity and rapid 

decompression of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Boeing supported the NPRM (79 FR 

30753, May 29, 2014). 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

30753, May 29, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 30753, 

May 29, 2014). 

Costs of Compliance 

We estimate that this AD affects 48 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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